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    CONDUIT PREHEATING CONTROL
    1.
    发明公开
    CONDUIT PREHEATING CONTROL 审中-公开

    公开(公告)号：EP4443050A1

    公开(公告)日：2024-10-09

    申请号：EP24161493.2

    申请日：2024-03-05

    申请人： General Electric Technology GmbH

    发明人： PATIÑO RODRIGUEZ, Juan Manuel

    IPC分类号： F22D1/36 ,  F01D19/00 ,  F01K17/02

    CPC分类号： F22D1/36 ,  F01K17/02 ,  F01D19/00 ,  F05D2270/30320130101 ,  F01D15/10 ,  F05D2220/7620130101 ,  F05D2270/08220130101 ,  F05D2260/232220130101

    摘要： A conduit (104) is preheated with steam having steam drain valve(s) (DV1-DV2) therein open to allow draining and control valve(s) (CV1-CV2) therein closed to prevent steam downstream flow. A gas may backfill the conduit (104) from downstream gas source to further preheat, and gas drain valve(s) (DV3-DV4) may be provided to drain the gas. A predicted exit temperature (TE) of the steam or gas for a respective drain valve is calculated using a linear regression model based on initial temperature (Ti) and pressure (Pi) of the steam and a Joule-Thompson cooling effect for the steam or gas at the respective drain valve. The preheating is stopped for the respective section of conduit (104) when one or a combination of the predicted exit temperatures (TE) is greater than or equal to a respective required exit temperature of the steam or gas at a respective drain valve. The method and system may sequentially ensure adequate preheating of sections of the conduit (104).

    SYSTEME DE CONFIRMATION DE COUPURE D'UN MOTEUR D'AERONEF
    5.
    发明公开
    SYSTEME DE CONFIRMATION DE COUPURE D'UN MOTEUR D'AERONEF 审中-公开

    公开(公告)号：EP3909860A1

    公开(公告)日：2021-11-17

    申请号：EP21165261.5

    申请日：2021-03-26

    申请人： AIRBUS OPERATIONS (S.A.S.)

    发明人： ZACCARIA, Patrick ,  BOYER, David

    IPC分类号： B64D37/32 ,  F02C9/26 ,  B64D31/00 ,  G05B9/02 ,  F02C7/22 ,  B64D31/14 ,  F01D19/00 ,  F02C7/232

    摘要： Pour contrôler une coupure moteur dans un aéronef (100), un système de contrôle (110) comporte un organe de coupure d'alimentation en carburant (120) ; un organe de commande, qui comporte un ensemble d'interrupteurs, un premier interrupteur sur un lien d'alimentation électrique (130) de l'organe de coupure d'alimentation en carburant et une pluralité de seconds interrupteurs connectés à une avionique de l'aéronef, l'ensemble d'interrupteurs basculant de position sur commande de coupure moteur. Une unité de confirmation de coupure moteur comporte un troisième interrupteur placé sur le lien d'alimentation électrique, le troisième interrupteur étant par défaut en position ouverte. L'unité de confirmation de coupure moteur comporte de la circuiterie électronique configurée pour faire basculer le troisième interrupteur en position fermée lorsqu'une quantité prédéfinie Q d'interrupteurs de l'organe de commande bascule de position dans une fenêtre glissante de durée prédéfinie et, autrement, maintient le troisième interrupteur en position ouverte. Ainsi, il est assuré que la coupure moteur est intentionnelle.

    METHOD AND SYSTEM FOR CONTROLLING A PNEUMATIC VALVE
    8.
    发明公开
    METHOD AND SYSTEM FOR CONTROLLING A PNEUMATIC VALVE 审中-公开

    公开(公告)号：EP3715606A1

    公开(公告)日：2020-09-30

    申请号：EP20166402.6

    申请日：2020-03-27

    申请人： Pratt & Whitney Canada Corp.

    发明人： WALZ, Andrew ,  TANJU, Mehmet

    IPC分类号： F02C7/277 ,  F01D19/00

    摘要： Methods and systems (200) for controlling a pneumatic starter air valve (210) of a gas turbine engine are described herein. The starter air valve (210) is controlled in a first mode of operation by actuating a first solenoid (201) of the starter air valve (210) with a steady-state input signal. Passage of the steady-state input signal to a second solenoid (202) of the starter air valve (210) is allowed, to actuate the second solenoid (202) and enable pressure regulation of the starter air valve (210). The starter air valve (210) is controlled in a second mode of operation by actuating the first solenoid (201) with a pulse-width modulation input signal. Passage of the pulse-width modulation input signal to the second solenoid (202) is prevented, to disable the pressure regulation in the second mode of operation.

    METHOD FOR OPERATING A GAS TURBINE POWER PLANT AND GAS TURBINE POWER PLANT
    9.
    发明公开
    METHOD FOR OPERATING A GAS TURBINE POWER PLANT AND GAS TURBINE POWER PLANT 审中-公开

    公开(公告)号：EP3683426A1

    公开(公告)日：2020-07-22

    申请号：EP19151980.0

    申请日：2019-01-15

    申请人： Ansaldo Energia Switzerland AG

    发明人： APPEL, Christoph ,  SINGLA, Ghislain ,  FUX, Samuel ,  MÜLLER, Eric

    IPC分类号： F02C9/34 ,  F01D19/00 ,  F01D21/00 ,  F02C6/00

    摘要： A method for operating a gas turbine power plant; the gas turbine power plant (1) comprising a compressor (2), a sequential combustor assembly (3) and a turbine (4) arranged downstream the combustor assembly (3); the sequential combustor assembly (3) comprises a first combustor (10) and a second combustor (12) arranged downstream the first combustor (10); wherein between the first combustor (10) and the second combustor (12) a mixer (9) or a high pressure turbine is arranged; wherein the second combustor (12) comprises at least one combustion stage (7b, 7c); the method comprising:
    - operating the gas turbine power plant (1) at partial load;
    - during the partial load operation, supplying a first fuel flow rate to the first combustor (10) and subsequently igniting or switching off at least one combustion stage (7b, 7c) of the second combustor (12);
    - varying the first fuel flow rate when the combustion stage (7b; 7c) of the second combustor (12) is ignited or switched off so as to keep the variation of the power output of the gas turbine power plant (1) comprised in a compensation range; the compensation range being comprised between zero and an upper limit defined by the operative limits of the sequential combustor assembly (3) .